3D rocket combustor acoustics modelThe theory and procedures for determining the characteristics of pressure oscillations in rocket engines with prescribed burning rate oscillations are presented. Analyses including radial and hub baffles and absorbers can be performed in one, two, or three dimensions. Pressure and velocity oscillations calculated using this procedure are presented for the SSME to show the influence of baffles and absorbers on the burning rate oscillations required to achieve neutral stability. Comparisons are made between the results obtained utilizing 1D, 2D, and 3D assumption with regards to capturing the physical phenomena of interest and computational requirements.
Document ID
19920066205
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Priem, Richard J. (Priem Consultants, Inc. Cleveland, OH, United States)
Breisacher, Kevin J. (NASA Lewis Research Center Cleveland, OH, United States)